FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.96 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w270-il-1000000-n5.txt Download as CSV file: xf-fx77w270-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.1694 0.09905 0.09312 -0.0153 0.4883 0.0045
-19.500 -1.1770 0.09415 0.08811 -0.0173 0.4842 0.0045
-19.000 -1.1871 0.08537 0.07910 -0.0205 0.4770 0.0046
-18.750 -1.1897 0.08147 0.07511 -0.0217 0.4738 0.0046
-18.500 -1.1912 0.07775 0.07130 -0.0228 0.4704 0.0046
-18.250 -1.1913 0.07428 0.06773 -0.0237 0.4670 0.0046
-18.000 -1.1895 0.07113 0.06449 -0.0244 0.4635 0.0046
-17.500 -1.1839 0.06529 0.05847 -0.0254 0.4580 0.0047
-17.250 -1.1789 0.06270 0.05581 -0.0257 0.4563 0.0047
-17.000 -1.1734 0.06023 0.05327 -0.0259 0.4546 0.0047
-16.750 -1.1673 0.05788 0.05085 -0.0260 0.4530 0.0047
-16.500 -1.1601 0.05570 0.04860 -0.0260 0.4513 0.0047
-16.250 -1.1530 0.05356 0.04639 -0.0260 0.4497 0.0048
-16.000 -1.1440 0.05167 0.04444 -0.0259 0.4480 0.0048
-15.750 -1.1356 0.04974 0.04244 -0.0257 0.4463 0.0048
-15.500 -1.1258 0.04800 0.04064 -0.0254 0.4445 0.0048
-15.250 -1.1153 0.04638 0.03896 -0.0251 0.4427 0.0049
-15.000 -1.1056 0.04476 0.03728 -0.0247 0.4409 0.0049
-14.750 -1.0957 0.04320 0.03567 -0.0242 0.4392 0.0049
-14.500 -1.0843 0.04178 0.03421 -0.0237 0.4386 0.0049
-14.250 -1.0728 0.04037 0.03275 -0.0232 0.4380 0.0050
-14.000 -1.0615 0.03896 0.03130 -0.0226 0.4374 0.0050
-13.750 -1.0488 0.03768 0.02998 -0.0220 0.4366 0.0050
-13.500 -1.0360 0.03642 0.02868 -0.0215 0.4358 0.0050
-13.250 -1.0231 0.03515 0.02737 -0.0209 0.4349 0.0050
-13.000 -1.0092 0.03398 0.02616 -0.0203 0.4340 0.0051
-12.750 -0.9950 0.03284 0.02499 -0.0197 0.4329 0.0051
-12.500 -0.9811 0.03169 0.02380 -0.0190 0.4319 0.0051
-12.250 -0.9665 0.03059 0.02266 -0.0184 0.4308 0.0051
-12.000 -0.9518 0.02951 0.02154 -0.0177 0.4297 0.0052
-11.750 -0.9374 0.02841 0.02041 -0.0170 0.4285 0.0052
-11.500 -0.9235 0.02733 0.01929 -0.0161 0.4274 0.0052
-11.250 -0.9146 0.02617 0.01810 -0.0145 0.4263 0.0052
-11.000 -0.9033 0.02514 0.01703 -0.0133 0.4252 0.0053
-10.750 -0.8828 0.02427 0.01612 -0.0135 0.4239 0.0053
-10.500 -0.8593 0.02349 0.01530 -0.0142 0.4224 0.0053
-10.250 -0.8335 0.02279 0.01456 -0.0151 0.4209 0.0053
-10.000 -0.8063 0.02218 0.01392 -0.0162 0.4193 0.0054
-9.750 -0.7785 0.02165 0.01337 -0.0171 0.4188 0.0054
-9.500 -0.7502 0.02118 0.01288 -0.0179 0.4182 0.0054
-9.250 -0.7213 0.02075 0.01244 -0.0187 0.4174 0.0055
-9.000 -0.6919 0.02035 0.01203 -0.0196 0.4165 0.0055
-8.750 -0.6620 0.01998 0.01165 -0.0205 0.4155 0.0056
-8.500 -0.6316 0.01963 0.01129 -0.0215 0.4146 0.0056
-8.250 -0.6010 0.01931 0.01096 -0.0225 0.4137 0.0057
-8.000 -0.5700 0.01900 0.01064 -0.0235 0.4128 0.0058
-7.750 -0.5388 0.01871 0.01035 -0.0246 0.4118 0.0059
-7.500 -0.5073 0.01844 0.01007 -0.0257 0.4109 0.0060
-7.250 -0.4756 0.01818 0.00980 -0.0268 0.4099 0.0061
-7.000 -0.4437 0.01793 0.00954 -0.0279 0.4090 0.0063
-6.750 -0.4116 0.01768 0.00929 -0.0291 0.4080 0.0066
-6.500 -0.3794 0.01745 0.00907 -0.0303 0.4071 0.0069
-6.250 -0.3470 0.01719 0.00884 -0.0316 0.4061 0.0117
-6.000 -0.3146 0.01702 0.00866 -0.0328 0.4050 0.0130
-5.750 -0.2820 0.01687 0.00850 -0.0340 0.4037 0.0135
-5.500 -0.2495 0.01673 0.00836 -0.0352 0.4024 0.0138
-5.250 -0.2167 0.01657 0.00821 -0.0364 0.4013 0.0144
-5.000 -0.1840 0.01644 0.00808 -0.0377 0.4002 0.0149
-4.750 -0.1511 0.01629 0.00794 -0.0389 0.3999 0.0154
-4.500 -0.1182 0.01616 0.00781 -0.0402 0.3996 0.0158
-4.250 -0.0852 0.01603 0.00769 -0.0414 0.3992 0.0163
-4.000 -0.0522 0.01591 0.00758 -0.0427 0.3988 0.0166
-3.750 -0.0192 0.01579 0.00747 -0.0440 0.3983 0.0170
-3.500 0.0140 0.01565 0.00735 -0.0453 0.3978 0.0178
-3.250 0.0472 0.01554 0.00724 -0.0466 0.3972 0.0183
-3.000 0.0803 0.01543 0.00715 -0.0479 0.3965 0.0189
-2.750 0.1135 0.01534 0.00706 -0.0492 0.3957 0.0194
-2.500 0.1467 0.01524 0.00697 -0.0505 0.3947 0.0206
-2.250 0.1801 0.01511 0.00689 -0.0519 0.3937 0.0253
-2.000 0.2132 0.01504 0.00683 -0.0531 0.3926 0.0336
-1.750 0.2462 0.01498 0.00678 -0.0544 0.3917 0.0356
-1.500 0.2794 0.01492 0.00673 -0.0557 0.3908 0.0376
-1.250 0.3125 0.01486 0.00667 -0.0570 0.3899 0.0405
-1.000 0.3460 0.01475 0.00662 -0.0585 0.3891 0.0489
-0.750 0.3792 0.01469 0.00659 -0.0598 0.3883 0.0657
-0.500 0.4123 0.01465 0.00656 -0.0611 0.3874 0.0703
-0.250 0.4456 0.01458 0.00654 -0.0625 0.3864 0.0814
0.000 0.4788 0.01452 0.00652 -0.0639 0.3852 0.1034
0.250 0.5126 0.01441 0.00650 -0.0655 0.3838 0.1384
0.500 0.5466 0.01425 0.00648 -0.0673 0.3824 0.1862
0.750 0.5814 0.01400 0.00643 -0.0693 0.3815 0.2535
1.000 0.6190 0.01332 0.00624 -0.0723 0.3809 0.4009
1.250 0.6560 0.01270 0.00613 -0.0751 0.3803 0.5558
1.500 0.6889 0.01270 0.00624 -0.0764 0.3796 0.5836
1.750 0.7214 0.01279 0.00637 -0.0775 0.3789 0.5988
2.000 0.7538 0.01288 0.00648 -0.0786 0.3781 0.6087
2.250 0.7861 0.01297 0.00657 -0.0797 0.3773 0.6149
2.500 0.8184 0.01307 0.00665 -0.0808 0.3766 0.6184
2.750 0.8507 0.01315 0.00673 -0.0820 0.3758 0.6206
3.000 0.8829 0.01322 0.00682 -0.0831 0.3748 0.6230
3.250 0.9151 0.01331 0.00691 -0.0842 0.3737 0.6256
3.500 0.9471 0.01340 0.00702 -0.0853 0.3721 0.6292
3.750 0.9791 0.01350 0.00710 -0.0864 0.3699 0.6329
4.000 1.0110 0.01362 0.00719 -0.0875 0.3664 0.6358
4.250 1.0427 0.01378 0.00731 -0.0886 0.3631 0.6384
4.500 1.0747 0.01382 0.00738 -0.0897 0.3609 0.6423
4.750 1.1066 0.01389 0.00748 -0.0908 0.3584 0.6448
5.000 1.1384 0.01397 0.00756 -0.0919 0.3549 0.6456
5.250 1.1700 0.01406 0.00763 -0.0931 0.3499 0.6462
5.500 1.2013 0.01420 0.00774 -0.0942 0.3451 0.6468
5.750 1.2326 0.01433 0.00785 -0.0952 0.3397 0.6474
6.000 1.2636 0.01451 0.00800 -0.0963 0.3338 0.6482
6.250 1.2943 0.01472 0.00818 -0.0973 0.3285 0.6490
6.500 1.3251 0.01490 0.00835 -0.0984 0.3250 0.6498
6.750 1.3556 0.01510 0.00854 -0.0994 0.3214 0.6505
7.000 1.3858 0.01534 0.00876 -0.1004 0.3176 0.6511
7.250 1.4158 0.01558 0.00899 -0.1014 0.3140 0.6516
7.500 1.4462 0.01576 0.00918 -0.1024 0.3117 0.6521
7.750 1.4766 0.01592 0.00936 -0.1034 0.3097 0.6526
8.000 1.5068 0.01611 0.00956 -0.1043 0.3069 0.6530
8.250 1.5363 0.01635 0.00981 -0.1052 0.3024 0.6535
8.500 1.5647 0.01671 0.01014 -0.1060 0.2968 0.6539
8.750 1.5936 0.01698 0.01042 -0.1068 0.2922 0.6544
9.000 1.6180 0.01772 0.01105 -0.1072 0.2737 0.6548
9.250 1.6412 0.01853 0.01178 -0.1074 0.2598 0.6552
9.500 1.6655 0.01915 0.01236 -0.1076 0.2516 0.6556
9.750 1.6893 0.01976 0.01296 -0.1078 0.2445 0.6559
10.000 1.6960 0.02166 0.01469 -0.1059 0.2129 0.6563
10.250 1.7024 0.02326 0.01623 -0.1038 0.1986 0.6566
10.500 1.6854 0.02571 0.01869 -0.0983 0.1826 0.6569
10.750 1.6519 0.03028 0.02336 -0.0934 0.1723 0.6571
11.000 1.6170 0.03744 0.03067 -0.0928 0.1667 0.6574
11.250 1.5857 0.04457 0.03798 -0.0926 0.1654 0.6576
11.500 1.5450 0.05235 0.04595 -0.0916 0.1654 0.6577
11.750 1.5128 0.05887 0.05261 -0.0905 0.1662 0.6579
12.000 1.4791 0.06549 0.05937 -0.0894 0.1665 0.6580
12.250 1.4332 0.07355 0.06755 -0.0882 0.1634 0.6581
12.750 1.3828 0.08570 0.07979 -0.0875 0.1532 0.6584
13.000 1.3660 0.09094 0.08504 -0.0875 0.1471 0.6585
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Polar data table (+)
Polar graphs
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